XFOIL Version 6.96 Calculated polar for: GOE 683 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1053 0.07278 0.06900 -0.0721 1.0000 0.0375 -19.500 -1.1189 0.06792 0.06404 -0.0743 1.0000 0.0378 -19.250 -1.1294 0.06347 0.05950 -0.0764 1.0000 0.0381 -19.000 -1.1406 0.05904 0.05498 -0.0783 1.0000 0.0384 -18.750 -1.1492 0.05501 0.05084 -0.0800 1.0000 0.0386 -18.500 -1.1573 0.05115 0.04688 -0.0815 1.0000 0.0388 -18.250 -1.1588 0.04809 0.04372 -0.0825 1.0000 0.0391 -18.000 -1.1683 0.04433 0.03987 -0.0836 1.0000 0.0395 -17.750 -1.1774 0.04081 0.03628 -0.0843 1.0000 0.0399 -17.500 -1.1822 0.03793 0.03333 -0.0845 1.0000 0.0402 -17.250 -1.1828 0.03561 0.03095 -0.0843 1.0000 0.0407 -17.000 -1.1816 0.03360 0.02888 -0.0838 1.0000 0.0410 -16.750 -1.1768 0.03201 0.02725 -0.0830 1.0000 0.0415 -16.500 -1.1727 0.03049 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0.9147 2.500 0.5155 0.00886 0.00407 -0.0241 0.4042 0.9250 2.750 0.5534 0.00914 0.00433 -0.0261 0.3997 0.9266 3.000 0.5930 0.00943 0.00460 -0.0285 0.3959 0.9288 3.250 0.6297 0.00974 0.00487 -0.0302 0.3918 0.9320 3.500 0.6365 0.00990 0.00502 -0.0257 0.3883 0.9400 3.750 0.6840 0.01030 0.00537 -0.0297 0.3834 0.9412 4.000 0.7277 0.01053 0.00561 -0.0330 0.3799 0.9426 4.250 0.7676 0.01077 0.00583 -0.0355 0.3758 0.9442 4.500 0.8031 0.01101 0.00603 -0.0371 0.3713 0.9465 4.750 0.8107 0.01131 0.00631 -0.0328 0.3673 0.9541 5.000 0.8528 0.01146 0.00646 -0.0359 0.3639 0.9549 5.250 0.8924 0.01158 0.00657 -0.0384 0.3595 0.9558 5.500 0.9275 0.01173 0.00670 -0.0400 0.3545 0.9569 5.750 0.9628 0.01194 0.00687 -0.0417 0.3498 0.9586 6.000 0.9985 0.01209 0.00703 -0.0435 0.3465 0.9610 6.250 1.0120 0.01242 0.00737 -0.0405 0.3436 0.9678 6.500 1.0500 0.01246 0.00741 -0.0428 0.3391 0.9686 6.750 1.0843 0.01257 0.00749 -0.0444 0.3343 0.9696 7.000 1.1180 0.01268 0.00759 -0.0459 0.3300 0.9710 7.250 1.1507 0.01276 0.00768 -0.0471 0.3263 0.9728 7.500 1.1784 0.01291 0.00783 -0.0473 0.3221 0.9753 7.750 1.1846 0.01336 0.00827 -0.0430 0.3180 0.9806 8.000 1.2137 0.01335 0.00825 -0.0437 0.3124 0.9813 8.250 1.2440 0.01335 0.00826 -0.0445 0.3081 0.9822 8.500 1.2710 0.01342 0.00833 -0.0447 0.3035 0.9835 8.750 1.2913 0.01357 0.00845 -0.0436 0.2985 0.9852 9.000 1.3129 0.01365 0.00857 -0.0427 0.2949 0.9869 9.250 1.3314 0.01380 0.00873 -0.0412 0.2901 0.9890 9.500 1.3511 0.01414 0.00905 -0.0400 0.2852 0.9928 9.750 1.3786 0.01420 0.00911 -0.0405 0.2802 0.9941 10.000 1.4039 0.01429 0.00922 -0.0406 0.2748 0.9954 10.250 1.4258 0.01453 0.00943 -0.0402 0.2679 0.9975 10.750 1.4662 0.01502 0.00994 -0.0386 0.2563 1.0000 11.000 1.4679 0.01551 0.01043 -0.0344 0.2512 1.0000 11.250 1.4730 0.01597 0.01090 -0.0309 0.2458 1.0000 11.500 1.4755 0.01656 0.01150 -0.0272 0.2392 1.0000 11.750 1.4756 0.01732 0.01225 -0.0233 0.2321 1.0000 12.000 1.4782 0.01807 0.01300 -0.0200 0.2249 1.0000 12.250 1.4767 0.01907 0.01399 -0.0164 0.2166 1.0000 12.500 1.4738 0.02024 0.01513 -0.0128 0.2064 1.0000 12.750 1.4670 0.02172 0.01657 -0.0091 0.1926 1.0000 13.000 1.4652 0.02305 0.01789 -0.0062 0.1834 1.0000 13.250 1.4462 0.02550 0.02024 -0.0020 0.1633 1.0000 13.500 1.4287 0.02808 0.02275 0.0016 0.1473 1.0000 13.750 1.4147 0.03062 0.02526 0.0046 0.1371 1.0000 14.000 1.4094 0.03270 0.02736 0.0067 0.1324 1.0000 14.250 1.4067 0.03467 0.02936 0.0084 0.1296 1.0000 14.500 1.4003 0.03703 0.03174 0.0102 0.1257 1.0000 14.750 1.4007 0.03891 0.03368 0.0115 0.1238 1.0000 15.000 1.3974 0.04117 0.03598 0.0129 0.1213 1.0000 15.250 1.3955 0.04337 0.03823 0.0140 0.1201 1.0000 15.500 1.3883 0.04611 0.04101 0.0152 0.1174 1.0000 15.750 1.3846 0.04861 0.04356 0.0162 0.1161 1.0000 16.000 1.3800 0.05126 0.04625 0.0170 0.1139 1.0000 16.250 1.3798 0.05355 0.04861 0.0177 0.1131 1.0000 16.500 1.3799 0.05581 0.05093 0.0183 0.1115 1.0000 16.750 1.3780 0.05834 0.05352 0.0188 0.1104 1.0000 17.000 1.3737 0.06118 0.05641 0.0193 0.1088 1.0000 17.250 1.3691 0.06408 0.05936 0.0197 0.1073 1.0000 17.500 1.3602 0.06750 0.06282 0.0200 0.1054 1.0000 17.750 1.3511 0.07101 0.06639 0.0201 0.1037 1.0000 18.000 1.3528 0.07331 0.06875 0.0203 0.1029 1.0000 18.250 1.3540 0.07575 0.07125 0.0204 0.1016 1.0000 18.500 1.3543 0.07823 0.07379 0.0205 0.1000 1.0000 18.750 1.3498 0.08133 0.07694 0.0204 0.0983 1.0000 19.000 1.3463 0.08432 0.07996 0.0203 0.0965 1.0000